60804 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules 

fuel quantity indicating system (FQIS) wiring 

harness is routed correctly and relocate if 

necessary, in accordance with the 

Accomplishment Instructions of Bombardier 

Service Bulletin 8–28–52, dated November 3, 

2009. 

(i) Wire Routing Segregation and Installation 

of Dual Spacers—Part III 

Within 18,000 flight hours or 108 months, 

whichever occurs first, after the effective date 

of this AD, do the modification specified in 

paragraphs (i)(1) and (i)(2) of this AD, as 

applicable. 

(1) For airplanes having S/Ns 003 through 

672 inclusive, on which Modsum 8Q101513 

has been incorporated or on which Modsum 

8Q101652 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–36, dated August 9, 2006; Revision A, 

dated November 17, 2006; Revision B, dated 

February 12, 2008; or Revision C, dated 

October 7, 2009; excluding airplanes on 

which a long-range fuel system has been 

installed as specified in CF828CH00044, 

CR828SO08061, SOO 8061, CR828CH00027, 

or CR828SO00006: Accomplish Bombardier 

Modsum 8Q101908, ‘‘Fuel System—Fuel Qty 

Ind., Wire Routing Segregation, Installation 

of Dual Spacers—SFAR88 (Standard A/C),’’ 

Revision B, including installing dual spacers 

inside certain center fuselage locations, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–55, dated July 23, 2012. 

(2) For airplanes having S/Ns 003 through 

672 inclusive on which a long-range fuel 

system has been installed as specified in 

CF828CH00044, CR828SO08061, SOO 8061, 

CR828CH00027, or CR828SO00006, and on 

which Modsum 8Q902064 has been 

incorporated, or on which Modsum 

8Q902064 has been incorporated in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–42, dated December 21, 2008; or 

Revision A, dated October 1, 2008: 

Accomplish Bombardier Modsum 8Q902383, 

‘‘Fuel System—Fuel Qty Ind., Wire routing 

Segregation, Installation of Dual Spacers— 

SFAR88 (Long Range A/C),’’ Revision B, 

including installing dual spacers inside 

certain center fuselage locations, in 

accordance with the Accomplishment 

Instructions of Bombardier Service Bulletin 

8–28–56, dated July 23, 2012. 

(j) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (g)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–39, 

Revision A, March 15, 2007. 

(2) This paragraph provides credit for 

actions required by paragraph (g)(3) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–44, dated 

August 9, 2006; or Revision A, dated 

November 15, 2006. 

(3) This paragraph provides credit for 

actions required by paragraph (g)(6) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–41, 

Revision A, dated April 11, 2007. 

(4) This paragraph provides credit for 

actions required by paragraph (g)(8) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–43, dated 

August 10, 2006. 

(5) This paragraph provides credit for 

actions required by paragraph (g)(10) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–48, dated 

October 1, 2010. 

(6) This paragraph provides credit for 

actions required by paragraph (g)(13) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–49, dated 

October 1, 2010. 

(7) This paragraph provides credit for 

actions required by paragraph (h)(3) of this 

AD, if those actions were performed before 

the effective date of this AD using 

Bombardier Service Bulletin 8–28–53, dated 

November 3, 2008. 

(k) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, ANE–170, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the ACO, send it to ATTN: Program 

Manager, Continuing Operational Safety, 

FAA, New York ACO, 1600 Stewart Avenue, 

Suite 410, Westbury, NY 11590; telephone 

516–228–7300; fax 516–794–5531. Before 

using any approved AMOC, notify your 

appropriate principal inspector, or lacking a 

principal inspector, the manager of the local 

flight standards district office/certificate 

holding district office. The AMOC approval 

letter must specifically reference this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(l) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) Canadian 

Airworthiness Directive CF–2013–07, dated 

March 1, 2013, for related information, which 

can be found in the AD docket on the 

internet at http://www.regulations.gov. 

(2) For service information identified in 

this AD, contact Bombardier, Inc., Q-Series 

Technical Help Desk, 123 Garratt Boulevard, 

Toronto, Ontario M3K 1Y5, Canada; 

telephone 416–375–4000; fax 416–375–4539; 

email thd.qseries@aero.bombardier.com; 

Internet http://www.bombardier.com. You 

may review copies of this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Issued in Renton, Washington, on 

September 19, 2013. 

Ross Landes, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24077 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0836; Directorate 

Identifier 2013–NM–126–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to supersede 

airworthiness directive (AD) 2005–07– 

12 that applies to certain The Boeing 

Company Model 737–100, –200, –200C, 

–300, –400, and –500 series airplanes. 

AD 2005–07–12 requires detailed and 

eddy current inspections to detect 

cracking of the frame web around the 

cutout for the doorstop intercostal strap 

at the aft side of the station (STA) 291.5 

frame at stringer 16R, and corrective 

action if necessary. Since we issued AD 

2005–07–12, we received reports of new 

findings of cracking at various locations 

of the STA 277 to STA 291.5 frames and 

intercostals, including webs, chords, 

clips, and shear ties, between stringers 

7R and 17R. This proposed AD would 

add new inspections for cracking at the 

forward galley door cutout, and 

corrective actions if necessary. This 

proposed AD would also reduce a 

certain inspection threshold required by 

AD 2005–07–12. We are proposing this 

AD to detect and correct fatigue 

cracking of the aft frame and frame 

support structure of the forward galley 

door, which could result in a severed 

fuselage frame web, rapid 

decompression of the airplane, and 

possible loss of the forward galley door. 

DATES: We must receive comments on 

this proposed AD by November 18, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

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Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules 60805 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 

206–544–5000, extension 1; fax 206– 

766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Ave. 

SW., Renton, Washington. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; phone: 425– 

917–6450; fax: 425–917–6590; email: 

alan.pohl@faa.gov. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2013–0836; Directorate Identifier 

2013–NM–126–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD because of those 

comments. 

We will post all comments we 

receive, without change, to http://

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

On March 25, 2005, we issued AD 

2005–07–12, Amendment 39–14036 (70 

FR 17596, April 7, 2005), for certain The 

Boeing Company Model 737–100, –200, 

–300, –400, and –500 series airplanes. 

AD 2005–07–12 requires repetitive 

detailed and eddy current inspections to 

detect cracking of the frame web around 

the cutout for the doorstop intercostal 

strap at the aft side of STA 291.5 frame 

at stringer 16R, and corrective actions if 

necessary. We issued AD 2005–07–12 to 

detect and correct fatigue cracking of the 

aft frame and frame support structure of 

the forward galley door. 

Actions Since AD 2005–07–12, 

Amendment 39–14036 (70 FR 17596, 

April 7, 2005) Was Issued 

Since we issued AD 2005–07–12, 

Amendment 39–14036 (70 FR 17596, 

April 7, 2005) Boeing has received 24 

reports of cracking of the STA 291.5 

frame web around the doorstop 

intercostal strap cutout at stringer 16R. 

There have been 23 reports of cracks 

propagating down from the lower radius 

of the cutout on airplanes that had 

accumulated between 35,597 and 68,133 

total flight cycles. Boeing also received 

one report of a crack propagating 

outboard from the upper radius through 

two countersunk fastener locations on 

an airplane that had accumulated 

31,611 total flight cycles. In addition, 

Boeing received reports of cracking in 

other areas of the forward galley door 

cutout that are determined to be safety 

related. 

Relevant Service Information 

We reviewed Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013. For information on 

the procedures and compliance times, 

see this service information at http://

www.regulations.gov by searching for 

Docket No. FAA–2013–0836. 

FAA’s Determination 

We are proposing this AD because we 

evaluated all the relevant information 

and determined the unsafe condition 

described previously is likely to exist or 

develop in other products of the same 

type design. 

Proposed AD Requirements 

Although this proposed AD does not 

explicitly restate the requirements of AD 

2005–07–12, Amendment 39–14036 (70 

FR 17596, April 7, 2005) this proposed 

AD would retain all of the requirements 

of AD 2005–07–12. Those requirements 

are referenced in the service information 

identified previously, which, in turn, is 

referenced in paragraph (h) of this 

proposed AD. For certain airplanes, this 

proposed AD would reduce the 

compliance threshold for a certain 

inspection. This proposed AD would 

also require accomplishing the actions 

identified in the service information 

identified previously, except as 

discussed under ‘‘Differences Between 

the Proposed AD and the Service 

Information.’’ 

The phrase ‘‘corrective actions’’ is 

used in this proposed AD. ‘‘Corrective 

actions’’ are actions that correct or 

address any condition found. Corrective 

actions in an AD could include, for 

example, repairs. 

Differences Between the Proposed AD 

and the Service Information 

Boeing Alert Service Bulletin 737– 

53A1241, Revision 1, dated June 11, 

2013, specifies to contact the 

manufacturer for instructions on how to 

repair certain conditions, but this 

proposed AD would require repairing 

those conditions in one of the following 

ways: 

• In accordance with a method that 

we approve; or 

• Using data that meet the 

certification basis of the airplane, and 

that have been approved by the Boeing 

Commercial Airplanes Organization 

Designation Authorization (ODA) whom 

we have authorized to make those 

findings. 

Costs of Compliance 

We estimate that this proposed AD 

affects 419 airplanes of U.S. registry. 

We estimate the following costs to 

comply with this proposed AD: 

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60806 Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules 

ESTIMATED COSTS

Action Labor cost Parts cost Cost per product Cost on U.S. 

operators 

Inspections [retained from AD 2005–07– 

12, Amendment 39-14036 (70 FR 

17596)].

2 work-hours × $85 per hour = $170 per 

inspection cycle.

None ............ $170 per inspection 

cycle.

$71,230 per inspection cycle. 

Inspections [new proposed action] ......... 40 work-hours × $85 per hour = $3,400 

per inspection cycle.

None ............ $3,400 per inspection cycle.$1,424,600 per inspection cycle. 

We have received no definitive data 

that would enable us to provide a cost 

estimate for the on-condition actions 

specified in the service information. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

Section 106, describes the authority of 

the FAA Administrator. Subtitle VII, 

Aviation Programs, describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in Subtitle VII, 

Part A, Subpart III, Section 44701, 

‘‘General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This proposed 

regulation is within the scope of that 

authority because it addresses an unsafe 

condition that is likely to exist or 

develop on products identified in this 

rulemaking action. 

Regulatory Findings 

We have determined that this 

proposed AD would not have federalism 

implications under Executive Order 

13132. This proposed AD would not 

have a substantial direct effect on the 

States, on the relationship between the 

national Government and the States, or 

on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that the proposed regulation: 

(1) Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866, 

(2) Is not a ‘‘significant rule’’ under 

the DOT Regulatory Policies and 

Procedures (44 FR 11034, February 26, 

1979), 

(3) Will not affect intrastate aviation 

in Alaska, and 

(4) Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing airworthiness directive (AD) 

2005–07–12, Amendment 39–14036 (70 

FR 17596, April 7, 2005), and adding 

the following new AD: 

The Boeing Company: Docket No. FAA– 

2013–0836; Directorate Identifier 2013– 

NM–126–AD. 

(a) Comments Due Date 

The FAA must receive comments on this 

AD action by November 18, 2013. 

(b) Affected ADs 

This AD supersedes AD 2005–07–12, 

Amendment 39–14036 (70 FR 17596, April 7, 

2005). 

(c) Applicability 

This AD applies to The Boeing Company 

Model 737–100, –200, –200C, –300, –400, 

and –500 series airplanes, as identified in 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013. 

(d) Subject 

Joint Aircraft System Component (JASC)/

Air Transport Association (ATA) of America 

Code 53, Fuselage. 

(e) Unsafe Condition 

This AD was prompted by reports of new 

findings of cracking at various locations of 

the stations (STA) 277 to STA 291.5 frames 

and intercostals, including webs, chords, 

clips, and shear ties, between stringers 7R 

and 17R. We are issuing this AD to detect 

and correct fatigue cracking of the aft frame 

and frame support structure of the forward 

galley door, which could result in a severed 

fuselage frame web, rapid decompression of 

the airplane, and possible loss of the forward 

galley door. 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Group 1 Airplanes: Inspections and 

Corrective Actions 

For airplanes identified as Group 1 in 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013: Within 120 

days after the effective date of this AD, do 

inspections for cracking from STA 277 to 

STA 328, stringer 7R to 17R of the forward 

galley door cutout, using a method approved 

in accordance with the procedures specified 

in paragraph (l) of this AD. Do all applicable 

corrective actions before further flight using 

a method approved in accordance with the 

procedures specified in paragraph (l) of this 

AD. 

(h) Group 2 and Group 3 Airplanes: 

Inspections and Corrective Actions 

(1) For airplanes identified as Group 2 and 

Group 3 in Boeing Alert Service Bulletin 

737–53A1241, Revision 1, dated June 11, 

2013: Except as provided by paragraph (j)(2) 

of this AD, at the applicable times specified 

in tables 1 and 2 in paragraph 1.E, 

‘‘Compliance,’’ of Boeing Alert Service 

Bulletin 737–53A1241, Revision 1, dated 

June 11, 2013, do detailed and surface HFEC 

inspections, as applicable, for cracking in the 

forward galley door cutout, in accordance 

with Part 2 of the Accomplishment 

Instructions of Boeing Alert Service Bulletin 

737–53A1241, Revision 1, dated June 11, 

2013. Repeat the detailed and surface HFEC 

inspections thereafter at the applicable 

intervals specified in tables 1 and 2 in 

paragraph 1.E, ‘‘Compliance,’’ of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013. If any crack is found, 

before further flight, do all applicable 

corrective actions in accordance with Part 2 

of the Accomplishment Instructions of 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013, except as 

required by paragraph (j)(1) of this AD. Doing 

the repair in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, terminates the repetitive 

inspections required by this paragraph for the 

repaired area only. 

(2) Removal and replacement of a cracked 

part, in accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, does not terminate the 

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Federal Register / Vol. 78, No. 191 / Wednesday, October 2, 2013 / Proposed Rules 60807 

repetitive inspections required by paragraph 

(h)(1) of this AD. 

(i) Optional Terminating Action 

Accomplishment of the preventive 

modification on the STA 291.5 frame web, in 

accordance with Part 2 of the 

Accomplishment Instructions of Boeing Alert 

Service Bulletin 737–53A1241, Revision 1, 

dated June 11, 2013, terminates the repetitive 

inspections required by paragraph (h)(1) of 

this AD for the area that is common to the 

preventive modification. 

(j) Exceptions to the Service Information 

(1) Where Boeing Alert Service Bulletin 

737–53A1241, Revision 1, dated June 11, 

2013, specifies to contact Boeing for a 

corrective action: Before further flight, do the 

applicable action using a method approved 

in accordance with the procedures specified 

in paragraph (l) of this AD. 

(2) Where paragraph 1.E., ‘‘Compliance,’’ of 

Boeing Alert Service Bulletin 737–53A1241, 

Revision 1, dated June 11, 2013, specifies a 

compliance time ‘‘after the date on Revision 

1 of this service bulletin,’’ this AD requires 

compliance within the specified compliance 

time after the effective date of this AD. 

(k) Credit for Previous Actions 

This paragraph provides credit for the 

actions specified in paragraph (h)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Boeing 

Alert Service Bulletin 737–53A1241, dated 

June 13, 2002, which is not incorporated by 

reference in this AD. 

(l) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle Aircraft 

Certification Office (ACO), FAA, has the 

authority to approve AMOCs for this AD, if 

requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in 

paragraph (m) of this AD. Information may be 

emailed to: 9-ANM-Seattle-ACO–AMOCRequests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by the 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(4) AMOCs approved for the actions 

specified in AD 2005–07–12, Amendment 

39–14036 (70 FR 17596, April 7, 2005), are 

approved as AMOCs for the corresponding 

provisions of this AD. 

(m) Related Information 

(1) For more information about this AD, 

contact Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA Seattle 

Aircraft Certification Office, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6450; fax: 425–917– 

6590; email: alan.pohl@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, WA 98124–2207; telephone 206– 

544–5000, extension 1; fax 206–766–5680; 

Internet https://www.myboeingfleet.com. You 

may review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Ave. SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington on 

September 25, 2013. 

Jeffrey E. Duven, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2013–24040 Filed 10–1–13; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2013–0837; Directorate 

Identifier 2013–NM–112–AD] 

RIN 2120–AA64 

Airworthiness Directives; The Boeing 

Company Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

The Boeing Company Model 737–200, 

–200C, –300, –400, and –500 series 

airplanes. This proposed AD was 

prompted by reports of cracking found 

in the skin at the lower aft corner of the 

forward entry doorway on airplanes that 

do not have an airstair door cutout. This 

proposed AD would require repetitive 

inspections for cracking in the lower 

corners of the forward entry doorway on 

airplanes that do not have an airstair 

door cutout, and repair if necessary. We 

are proposing this AD to detect and 

correct cracking in the lower corners of 

the forward entry doorway, which could 

lead to crack progression and 

consequent rapid decompression of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by November 18, 

2013. 

ADDRESSES: You may send comments, 

using the procedures found in 14 CFR 

11.43 and 11.45, by any of the following 

methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: 202–493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC 20590. 

• Hand Delivery: Deliver to Mail 

address above between 9 a.m. and 5 

p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Boeing 

Commercial Airplanes, Attention: Data 

& Services Management, P. O. Box 3707, 

MC 2H–65, Seattle, WA 98124–2207; 

telephone 206–544–5000, extension 1; 

fax 206–766–5680; Internet https://

www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport 

Airplane Directorate, 1601 Lind Avenue 

SW., Renton, WA. For information on 

the availability of this material at the 

FAA, call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http://

www.regulations.gov; or in person at the 

Docket Management Facility between 9 

a.m. and 5 p.m., Monday through 

Friday, except Federal holidays. The AD 

docket contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Office 

(phone: 800–647–5527) is in the 

ADDRESSES section. Comments will be 

available in the AD docket shortly after 

receipt. 

FOR FURTHER INFORMATION CONTACT: 

Alan Pohl, Aerospace Engineer, 

Airframe Branch, ANM–120S, FAA, 

Seattle Aircraft Certification Office, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; phone: (425) 917–6450; 

fax: (425) 917–6590; email: alan.pohl@

faa.gov. 

SUPPLEMENTARY INFORMATION:

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposal. Send your comments to 

an address listed under the ADDRESSES

section. Include ‘‘Docket No. FAA– 

2013–0837; Directorate Identifier 2013– 

NM–112–AD’’ at the beginning of your 

comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

mstockstill on DSK4VPTVN1PROD with PROPOSALS